Submissible air-to-surface warhead with propellant-diaphragm deployment mechanism

ABSTRACT

A submissile warhead, which is part of a parent air-to-surface missile, incorporates a novel propellant-diaphragm deployment mechanism which causes the simultaneous ejection of a plurality of submissiles, each of which contains an explosive charge, from within the warhead at different velocities and, thereby, results in a large, controlled and uniform ground impact distribution pattern of the submissiles upon the designated enemy ground target, such as a surface-to-air missile site.

tJnite States atent m1 Boulter et al.

[ SUBMISSIBLE AlR-TO-SURFACE WARHEAD WITH PROPELLANT-DIAPHRAGM DEPLOYMENT MECHANISM [75] Inventors: Thomas W. Boulter, Maitland;

Bernard Van Zyl, Altamonte Springs, both of Fla.

[73] Assignee: The United States of America as represented by the Secretary of the United States Air Force, Washington, D.C.

[22] Filed: Dec. 20, 1971 [21] Appl. No.: 210,257

[52] U.S. Cl l02/7.2, l02/37.6, 102/68 [51] Int. Cl. F42b 25/16 [58] Field of Search 102/7.2, 4, 7.4, 8, 37.6,

[56] References Cited UNITED STATES PATENTS 3,332,348 7/l967 Myers et al. l02/7.2

[ Feb. 11, 1975 3,344,742 lO/l967 Schneider, Jr. 102/8 3,626,415 l2/l97l Montgomery l02/37.6 X 3,648,610 3/1972 Van Zyl et al [02/72 3,675,577 7/l972 Sternberg et al. 102/67 Primary Examiner-Samuel W. Engle Attorney, Agent, or Firm-Harry A. Herbett, Jr.; Arsen Tashjian [57] ABSTRACT A submissile warhead, which is part of a parent air-tosurface missile, incorporates a novel propellantdiaphragm deployment mechanism which causes the simultaneous ejection of a plurality of submissiles, each of which contains an explosive charge, from within the warhead at different velocities and, thereby, results in a large, controlled and uniform ground impact distribution pattern of the submissiles upon the designated enemy ground target, such as a surface-toair missile site.

3 Claims, 5 Drawing Figures INVENTOR5 THOMAS w. BOULTER PATENTEB FEB? l 1975 mm 2 OF 2 INVENTORS THOMAS w. scum-E 1 v SUBMISSIBLE AIR-TO-SURFACE WARIIEAD WITI'I PROPELLANTDIAPIIRAGM DEPLOYMENT MECHANISM I BACKGROUND OF THE INVENTION This invention relates generally toa busmissile warhead which is part of a parent (i.e., carrier) air-tosurface missile structures, and more particularly to a propellant-diaphragm deployment mechanism in the warhead for ejecting (i.e., deploying, dispersing, or projecting) a plurality of submissiles (i.e., mini-bombs, bomblets and the like) from within the warhead on to a designated enemy ground target.

It is obviously in the interest of national security that the U.S. Government have available for self-defense a submissile air-to-surface warhead from which a plurality of submissiles, each of which contain an explosive charge, are ejected in such a manner as to result in a large, controlled, uniform submissile ground impact distribution pattern upon an enemy target, especiallywhere the target is or includes a surface-to-air missile site.

Prior art techniques of submissile dispersal may be divided into three broad categories: dispersion by aerodynamic characteristics, dispersion by centrifugal means, and dispersion by chemical energy. Dispersion by aerodynamic characteristics includes spinning bodies, lifting bodies, winged bodies, parachutes and webbing catapult systems. These systems provide small, random, uncontrolled grouped impact patterns usually with an area near the center containing no submissiles. The second category in the dispersion of submissiles by spinning a container at high speed prior to release. This system in general requires complex, precision subsystems of high parasitic weight and volume resulting in high unit cost. The third category, dispersal by chemical energy, includes ejection of submissiles from containers by means of a propelling system within the container or by a self-contained propulsion system within the munition. Since the submissile should be made as small as possible, to achieve high packing density, a self-contained propulsion system is impractical. Therefore, a propelling system within the container that would provide a large, controlled, uniform submissile ground impact pattern is desired and is needed.

Several propelling system techniques have previously been used. These include the mortar technique, spigot technique, clamshell technique, rubber sleeve, and blast technique. The first two systems, mortar and spigot techniques, are both highly efficient in converting a high percentage of the available chemical energy to submissile kinetic energy. They provide controllable submissle ejection velocities in any range desired. However, both systems are complex, heavy, costly, and require large parasitic volumes. The clamshell technique requires both high parasitic weight and volume and results in relatively low velocity ranges (less than 100 feet per second). The rubber sleeve technique and blast technique are both low efficiency systems and provide high impact loading to the submissiles. Therefore, considerable buffering material is required to reduce the impact loads and large parasitic volumes result. Also, high, uncontrolled ejection velocities are obtained.

Therefore, there exists a genuine and critical need for a submissile air-to-surface warhead which includes a simple, moderate cost, minimal weight submissile deployment mechanism of the propelling system type to provide a positive and controlled deployment of the charge-containing submissiles, such that the plurality of submissiles housed within the warhead will be ejected from the warhead simultaneously and with different velocities and will result in the desired large and uniform ground impact distribution pattern of the submissiles on the target. The submissile warhead and the deployment mechanism also should provide low impact loading to the submissiles; should have a low parasitic volume; and should permit the use of submissiles of almost any configuration.

We have invented a submissile warhead which incor porates such a submissile deployment mechanism and thereby have fulfilled the need and significantly advanced the state-of-the art. In addition, our invention converts approximately percent of the available chemical energy of the propellant used into kinetic energy, instead of the 16 percent which is usually converted by prior art devices, and we have thereby further advanced the state-of-the art.

SUMMARY OF THE INVENTION This invention relates to a submissile air-to-surface warhead which incorporates a simple, moderate cost, minimal weight propellant-diaphragm deployment mechanism for simultaneously ejecting at different v'elocities a plurality of submissiles, each of which contain an explosive charge, onto an enemy ground target, especially a surface-to-air missile site, in a large, controlled and uniform ground impact distribution pattern. The invention also permits low impact loading to the submissiles, low parasitic volume and the use of submissiles of almost any configuration.

Therefore, the principal object of this invention is to provice such a submissile warhead with such a propellam-diaphragm deployment mechanism.

This principal object, and still other and related ones of this invention, will become readily apparent after a consideration of the description of the invention and reference to the drawings.

DESCRIPTION OF TI-IEDRAWING FIG. 1 is a perspective view, in schematic form and partially fragmented, of a preferred embodiment of the submissile warhead;

FIG. 2 is an end elevation view, in schematic form and partially fragmented, of the preferred embodiment shown in FIG. 1;

FIG. 3 is a side elevation view, in crosssection and in schematic form, of the preferred embodiment shown in FIGS. 1 and 2, taken along line 3-3 of FIG. 2;

FIG. 4 is a side elevation view, enlarged and in detail in cross-section, in schematic form, and partially fragmented, of a preferred embodiment of the igniterinitiator explosive charge of the propellant charge explosive train used in the submissile warhead; and

FIG. 5 is a perspective view, in schematic form, of the ejection of the submissiles from the warhead.

DESCRIPTION OF THE PREFERRED EMBODIMENT With reference to FIG. 1, there is shown a perspective view, in schematic form and partially fragmented, of a preferred embodiment 10 of the submissile warhead. The preferred embodiment 10 includes, as shown in FIG. 1: a hollow open-ended cylindrical casing or sheath 11 of frangible material, preferably of Plexiglas;

first circular end plate 12, preferably of heat treated aluminum, connected to and closing the open end 13 of cylindrical casing 11; second circular end plate 14, preferably of heat treated aluminum, connected to and closing the other open end 15 of cylindrical casing 11; centrally located propellant chamber 40; rubber diaphragm 90, preferably 0.25 inch thick and made of what is known in the art as RTV-630" silicon rubber; and a plurality of submissiles 100 circumferentially arranged in multiple radial layers, around rubber diaphragm 90, in the space between the outer surface of rubber diaphragm 90 and the inner surface of casing 11. It is to be noted, in connection with the submissiles 100, that although they are depicted in FIG. 1 as being cylindrical in form, this is merely by way of illustration and not by way of limitation. The submissiles, such as 100, may be of almost any configuration.

In FIG. 2 is shown an end elevation view, in schematic form and partially fragmented, of the preferred embodiment depicted in FIG. 1. Shown in FIG. 2 are: cylindrical casing or sheath 11; second circular end plate 14 connected to, abutting the inner periphery of, and closing open end 15 of casing 11; a plurality of retainers or fasteners, such as 16A, 16B, 16C, 16D and 16E, passing into and through suitable openings in second circular end plate 14; aperture 17 in second circular end plate 14, with protuberance 51 of second end cap 52, which said end cap is preferably of steel, fitting therein; aperture or longitudinal passage 53 in second end cap 52, with igniter explosive charge 23, preferably of the cord-type, such as is known in the art as 820 Pyrocore" and is manufactured by the duPont deNemours Co., therein; propellant chamber tube 41, preferably of steel; annular expansion chamber 60, concentric to and surrounding propellant chamber tube 41; structural or support tube 70, preferably of steel, of a larger diameter than, and concentric to and surrounding, propellant tube 41 and defining the outer surface of annular expansion chamber 60; metal diaphragm or shell 80, preferably of corrugated soft aluminum alloy and in the form of a hollow open-ended cylinder, of a larger diameter than, and concentric to and surrounding, structural tube 70; rubber diaphragm 90, which is circular in cross-section in its unexpanded state, of a diameter larger than, and concentric to and surrounding, metal diaphragm 80; and a plurality of submissiles 100, circumferentially arranged, in multiple radial layers, around diaphragm 90, in the annular space between diaphragm 90 and casing 11. It is again here emphasized that, although the submissiles 100 are shown in FIG. 2. as having a circular end view, this is only by way of illustration. Submissiles of any end view configuration may be used.

FIG. 3 is a side elevation view, in cross-section and in schematic form, of the preferred embodiment 10 shown in FIGS. 1 and 2, taken along line 3-3 of FIG. 2. As shown in FIG. 3, and in conjunction with FIGS. 1 and 2, in all of which FIGS. the same component has the same reference numeral, submissile warhead 10 is, externally, essentially a close-ended right circular cylinder housing which is defined and formed by openended cylindrical casing 11, and first 12 and second 14 circular end plates which close, respectively, open end 13 of casing 11 and other open end 15 of casing 11. Circular end plates 12 and 14 fit into, abut the inner periphery of, and are connected to casing 11 at the respective open ends 13 and 15. First circular end plate 12 has, at its geometric center, an aperture 19. Similarly, second circular end plate 14 has at its geometric center, an aperture 17. Protuberance 54 of first end cap 55, which is preferably of steel, fits into and mates with aperture 19 of first circular end plate 12. Similarly, protuberance 51 of second end cap 52 fits into and mates with aperture 17 of second circular end plate 14. Second end cap 52 has an aperture or longitudinal passage 53 therein which is aligned with aperture 17 of second circular end plate 14, and which contains in said passage 53 a portion of the length of the cord-type igniter 23 that is, thereby accessible external of second end cap 52. Rubber diaphragm 90 is, in its unexpanded state, in the shape of a hollow close-ended cylinder having an aperture 91 at one end and an aperture 92 at the other end. Rubber diaphragm 90 is constrained and retained in longitudinal position at one end by and between, first end cap 55 and first circular end plate 12 which, in turn, are connected to each other by suitable means, such as fasteners or retainers 18A and 18B. Rubber diaphragm 90 is similarly constrained and retained in a longitudinal position at the other end by and between, second end cap 53 and second circular end plate 14 which, in turn, are connected to each other by suitable means, such as fasteners or retainers 16C and 16F (and 16A, 16B, 16D and 16B of FIG. 2). As can be seen, protuberance 54 of first end cap 55 passes through aperture 91 of rubber diaphragm 90, and protuberance 51 of second end cap 52 passes through aperture 92 of rubber diaphragm 90. First end cap 55 and second end cap 52 are internal of rubber diaphragm 90, and first circular end plate 12 and second circular end plate 14 are external to rubber diaphragm 90.

Still with reference to FIG. 3, soft aluminum alloy diaphragm or shell is in the form of a corrugated hollow open-ended cylinder; is located internal of rubber diaphragm in a longitudinal position; is concentric with and abuts rubber diaphragm 90; and is disposed between and secured and closed at each end respectively by, first end cap 55 and second end cap 52. Structural or support tube 70 is longitudinally positioned concentric with, adjacent to, and internal of diaphragm 80; has a plurality of ports, such as 71 and 72, preferably 16, in its wall; and is disposed between, secured and closed at each end respectively by, first end cap 55 and second end cap 52. Propellant chamber tube 41 is longitudinally positioned concentric with, and internal of, structural tube 70; has a plurality of ports, such as 42 and 43, preferably 36, in its wall; and is disposed between, secured and closed at each end respectively by, first end cap 55 and second cap 52, except for aperture or longitudinal passage 53. Annular expansion chamber 60 is formed by the inner surface of structural tube 70, the outer surface of propellant chamber tube 41, and the inner surface of first and second end caps 55 and 52. Disposed in the annular space formed by the outer surface of rubber diaphragm 90, the inner surface of casing 11 and the inner surface of first and second circular end plates 12 and 14, are a plurality of submissiles circumferentially arranged, in multiple radial layers, around rubber diaphragm 90.

Again with reference to FIG. 3, propellant chamber 40 is formed by the inner surface off propellant chamber tube 41 and the inner surface of first and second end caps 55 and 52. Disposed within propellant chamber 40, and of course propellant chamber tube 41, is propellant charge explosive train assembly 30. The explosive train assembly includes a suitable propellant 31, (i.e., propellant charge) the purpose or function of which is to produce (i.e., generate) gas. It is here to be' noted that the term propellant is intented to mean and to include, but not be limited to, not only a single constituent propellant, but also a mixture or a compound of a plurality of propellant constituents. In fact, a propellant mixture or charge consisting of equal parts by weight of what is known and designated in the art as SR4990 propellant manufactured by duPont deNemours & Co. and of M-lO propellant is preferred. Alternatively, a propellant mixture or charge consisting of equal parts by weight of what is known and designated in the art as Red Dot" propellant, which is manufactured by Hercules, Inc. and of M-lO propellant is preferred. Centrally positioned within propellant 31 and part of assembly 30 is igniter-initiator charge subassembly 20 which includes tube 21, preferably of thin wall plastic, containing igniter-initiator explosive charge 22.

With reference to FIG. 4, there is shown in side elevation view enlarged and in detail, in cross-section, in schematic form and partially fragmented, a preferred embodiment of the propellant charge explosive train igniter-initiator charge subassembly 20 used in propellant chamber 40, FIG. 3, with propellant 31, FIG. 3. Within igniter-initiator tube 21 is igniter-initiator explosive charge 22 which includes centrally located igniter explosive charge 23, preferably of the cord-type, such as is known and is designated in the arts as 820 Pyrocore, surrounded by an initiator explosive charge 24, preferably a mixture of boron potassium nitrate. Igniter 23 has a covering or wrapping 25 within which igniter 23 is contained and confined prior to activation. It is here again noted that a portion of the length of igniter 23 with covering 25 is positioned in passage 53 of second end cap 52, FIGS. 2 and 3; is not surrounded by initiator 24; and is accessible external of second end cap 52.

With reference to FIG. 5, therein is shown a perspective view, in schematic form, of the ejection, i.e., deployment of the plurality of submissiles 100 from the warhead. Also shown are first circular end plate 12, second circular end plate 14, and rubber diaphragm 90 which is constrained and retained at each end, and which has expanded radially and differentially, i.e., has expanded the greatest or most at the center thereof.

Again with reference to FIG. 5, it is emphasized that although the submissiles 100 are shown therein as cylindrical in form, this is by way of illustration only. Submissiles of any configuration may be used.

Therefore, in summary and with reference to FIGS. 1-5, the preferred embodiment of our submissile warhead may be said to comprise: a housing formed by frangible open-ended cylindrical casing 11 and by first circular end plate 12 and second circular end plate 14; a plurality of submissiles, such as 100, each containing an explosive charge, with the submissiles circumferentially arranged within the housing in multiple radial layers; and a propellant-diaphragm deployment mechanism, centrally located within the housing and radially surrounded by submissiles, for ejecting the submissiles from the housing simultaneously and at different velocities, so that a controlled, large and uniform ground impact distributionpattern of the submissiles is obtained on the target. The propellant-diaphragm deployment mechanism may, in the interest of simplicity and brevity, be said to include but not be limited to: rubber diaphragm 90, constrained and retained at each end; corrugated soft aluminum alloy diaphragm 80 concentric with, within, andabutting rubber diaphragm 90; structural tube 70, with ports, concentric with, within, and abutting diaphragm 80; propellant chamber tube 41, with ports, and with propellant chamber 40 therein, with tube 41 concentric with and within structural tube 70, annular expansion chamber 60 formed by the inner surface of structural tube 70 and the outer surface of propellant chamber tube 41; suitable means, such as end caps 55 and 52 for closing each end of, and securing in concentric relationship, rubber diaphragm 90,

metal diaphragm 80, structural tube 70, and propellant chamber tube 41; and a suitable propellant charge explosive train assembly 30 disposed within propellant chamber 40 of tube 41.

MODE OF OPERATION OF THE PREFERRED EMBODIMENT When the parent (i.e., carrier) air-to-surface missile is released from its source, such as an aircraft over or near the designated target, the submissile warhead 10 is, in turn, subsequently launched, dropped, or the like, from the parent missile and the propellant charge explosive train, FIGS. 3 and 4, is activated. Since neither the parent missile nor the means for activating the propellant charge explosive train 30 form any part of this invention and since an understanding of either is not necessary for an understanding of this invention, neither will be described or explained herein.

More specifically, cord-type igniter 23 with covering 25, FIGS. 3-5, is activated by suitable conventional means not part of this invention. As a result igniter 23 fragments, burns, and the like, covering 25 and ignites the initiator charge 24, FIG. 4. Then, the initiator charge 24 fragments, burns, and the like, igniterinitiator tube 21, FIGS. 3 and 4, and ignites propellant 31 FIG. 3. In turn, propellant 31 burns and generates a gas which is exhausted through ports, such as 42 and 43, FIG. 3, of propellant chamber tube 41, FIGS. 2 and 3. The gas generated by the burning of propellant 31 is exhausted through the propellant chamber tube ports and flows into annular expansion chamber 60, FIGS. 2 and 3, at a rate determined by choked flow. The gas is expanded and cooled in chamber 60. The gas then flows through the ports, such as 71 and 72, FIG. 3, of structural or support tube 70, FIGS. 2 and 3, and into the volume behind corrugated metal diaphragm 80, FIGS. 2 and 3. It is here to be noted that metal diaphragm prevents the propellant gases from coming into direct contact with rubber diaphragm 90, FIGS. 1, 2, 3 and 5, since the gases would be detrimental to the rubber diaphragm in that they might cause damage and premature rupture to rubber diaphragm 90. As gas pressure increases metal diaphragm 80 and rubber diaphragm 90 expand radially and provide the energy to accelerate submissiles 100, FIGS. 1, 2, 3 and 5, without high impact loading of the submissiles 100. The energy imparted through submissiles shatters casing 11, FIGS. l-3, thereby permitting ejection of the submissiles 100. Since rubber diaphragm 90 is constrained and retained at each end, differential expansion of diaphragm 90 occurs over its entire length, thereby varying the ejection velocity of each of the submissiles 100.

As a result, a large, controlled, uniform ground impact distribution pattern of the submissiles 100 is obtained on the target.

As a related matter, it is to be noted that two full scale models of the preferred embodiment 10 of the submissile warhead were fabricated and tested. Each of these warheads was 12.12 inches in diameter, 21.5 inches long, and weighed approximately 150 pounds. Five hundred sixty-seven 95-gram simulated submissiles of cylindrical configuration were packaged, i.e., circumferentially arranged in multiple radial layers, in the annular space formed by the outer surface of rubber diaphragm 90, FIGS. 1, 2, 3 and 5, the inner surface of casing 11, FIGS. l-3, which in these models was of Plexiglass, the inner surface of first circular end plate 12, FIGS. 1, 3 and 5, and the inner surface of second circular end plate 14, FIGS. 1, 2, 3 and 5. In one test mode] a propellant mixture of 50 grams of M-lO propellant and 50 grams of SR 4990 propellant was used. Each model tested resulted in the desired controlled, large, uniform submissible impact pattern.

While there have been shown and described the fundamental features of our invention, as applied to a preferred embodiment and as adapted for a particular use, it is to be understood that various substitutions, omissions and adaptations may be made by those of ordinary skill in the art without departing from the spirit of the invention. For example, our invention may be used, or can be adapted to be used, with or in a suitable ordnance item, other than an air-to-surface missile structure.

What we claim is 1. A submissile warhead, adapted for use with a parent air-to-surface missile structure from which said warhead is launched onto a designated ground target, comprising:

a. a housing which includes:

1. a hollow open-ended cylindrical casing of frangible material;

2. a first circular end plate connected to and closing one open end of said casing;

3. a second circular end plate connected to and closing the other open end of said casing;

b. a plurality of submissiles positioned within said housing, with each of said plurality of submissiles containing an explosive charge, and with the said plurality of submissiles circumferentially arranged, within said housing, in multiple radial layers;

c. and, means, disposed within said housing, for ejecting said plurality of submissiles, simultaneously and at different velocities, from within said housing, with said means centrally located within said housing and radially surrounded by said plurality of submissiles, and wherein said means includes:

1. a rubber diaphragm in the unexpanded shape of a hollow close-ended cylinder having an aperture at each end, with said rubber diaphragm disposed within and concentric with said casing of said housing, and with said rubber diaphragm constrained and retained at each end by suitable means which also closes the apertures of said rubber diaphragm;

2. a soft aluminum alloy diaphragm in the unexpanded shape of a corrugated hollow open-ended cylinder, with said soft aluminum alloy diaphragm positioned internal of, concentric with, and abutting said rubber diaphragm, and with said soft aluminum alloy diaphragm disposed between and secured and closed at each end by suitable means;

3. a steel structural tube with a plurality of ports in its wall, with said structural tube positioned internal of, concentric with, and abutting said soft aluminum alloy diaphragm, and with said structural tube disposed between and secured and closed at each end by suitable means;

4. a steel propellant chamber tube with a plurality of ports in its wall, with said propellant chamber tube positioned internal of and concentric with said steel structural tube, and with said propellant fchamber tube disposed between and secured and closed at each end by suitable means;

5. and, a propellant charge explosive train, for generating gas, disposed essentially within said propellant chamber tube, wherein said propellant charge explosive train includes: aa. an igniter explosive charge; bb. an initiator explosive charge radially surrounding said igniter explosive charge; cc. and, a propellant explosive charge radially surrounding said initiator explosive charge; whereby when said submissiles are ejected from said housing, they form a controlled, large, uniform ground impact distribution pattern on the target.

2. Means for ejecting said plurality of submissiles from within said housing, as set forth in claim 1, wherein said igniter explosive charge of said propellant charge explosive train is of the cord-type.

3. Means for ejecting said plurality of submissiles from within said housing, as set forth in claim 1, wherein said initiator explosive charge is a mixture of boron potassium nitrate. 

1. A submissile warhead, adapted for use with a parent air-tosurface missile structure from which said warhead is launched onto a designated ground target, comprising: a. a housing which includes:
 1. a hollow open-ended cylindrical casing of frangible material;
 2. a first circular end plate conneCted to and closing one open end of said casing;
 3. a second circular end plate connected to and closing the other open end of said casing; b. a plurality of submissiles positioned within said housing, with each of said plurality of submissiles containing an explosive charge, and with the said plurality of submissiles circumferentially arranged, within said housing, in multiple radial layers; c. and, means, disposed within said housing, for ejecting said plurality of submissiles, simultaneously and at different velocities, from within said housing, with said means centrally located within said housing and radially surrounded by said plurality of submissiles, and wherein said means includes:
 1. a rubber diaphragm in the unexpanded shape of a hollow close-ended cylinder having an aperture at each end, with said rubber diaphragm disposed within and concentric with said casing of said housing, and with said rubber diaphragm constrained and retained at each end by suitable means which also closes the apertures of said rubber diaphragm;
 2. a soft aluminum alloy diaphragm in the unexpanded shape of a corrugated hollow open-ended cylinder, with said soft aluminum alloy diaphragm positioned internal of, concentric with, and abutting said rubber diaphragm, and with said soft aluminum alloy diaphragm disposed between and secured and closed at each end by suitable means;
 3. a steel structural tube with a plurality of ports in its wall, with said structural tube positioned internal of, concentric with, and abutting said soft aluminum alloy diaphragm, and with said structural tube disposed between and secured and closed at each end by suitable means;
 4. a steel propellant chamber tube with a plurality of ports in its wall, with said propellant chamber tube positioned internal of and concentric with said steel structural tube, and with said propellant fchamber tube disposed between and secured and closed at each end by suitable means;
 5. and, a propellant charge explosive train, for generating gas, disposed essentially within said propellant chamber tube, wherein said propellant charge explosive train includes: aa. an igniter explosive charge; bb. an initiator explosive charge radially surrounding said igniter explosive charge; cc. and, a propellant explosive charge radially surrounding said initiator explosive charge; whereby when said submissiles are ejected from said housing, they form a controlled, large, uniform ground impact distribution pattern on the target.
 2. Means for ejecting said plurality of submissiles from within said housing, as set forth in claim 1, wherein said igniter explosive charge of said propellant charge explosive train is of the cord-type.
 2. a soft aluminum alloy diaphragm in the unexpanded shape of a corrugated hollow open-ended cylinder, with said soft aluminum alloy diaphragm positioned internal of, concentric with, and abutting said rubber diaphragm, and with said soft aluminum alloy diaphragm disposed between and secured and closed at each end by suitable means;
 2. a first circular end plate conneCted to and closing one open end of said casing;
 3. a steel structural tube with a plurality of ports in its wall, with said structural tube positioned internal of, concentric with, and abutting said soft aluminum alloy diaphragm, and with said structural tube disposed between and secured and closed at each end by suitable means;
 3. a second circular end plate connected to and closing the other open end of said casing; b. a plurality of submissiles positioned within said housing, with each of said plurality of submissiles containing an explosive charge, and with the said plurality of submissiles circumferentially arranged, within said housing, in multiple radial layers; c. and, means, disposed within said housing, for ejecting said plurality of submissiles, simultaneously and at different velocities, from within said housing, with said means centrally located within said housing and radially surrounded by said plurality of submissiles, and wherein said means includes:
 3. Means for ejecting said plurality of submissiles from within said housing, as set forth in claim 1, wherein said initiator explosive charge is a mixture of boron potassium nitrate.
 4. a steel propellant chamber tube with a plurality of ports in its wall, with said propellant chamber tube positioned internal of and concentric with said steel structural tube, and with said propellant fchamber tube disposed between and secured and closed at each end by suitable means;
 5. and, a propellant charge explosive train, for generating gas, disposed essentially within said propellant chamber tube, wherein said propellant charge explosive train includes: aa. an igniter explosive charge; bb. an initiator explosive charge radially surrounding said igniter explosive charge; cc. and, a propellant explosive charge radially surrounding said initiator explosive charge; whereby when said submissiles are ejected from said housing, they form a controlled, large, uniform ground impact distribution pattern on the target. 